EP2578941A2 - Système d'injection de carburant dans un injecteur de carburant - Google Patents

Système d'injection de carburant dans un injecteur de carburant Download PDF

Info

Publication number
EP2578941A2
EP2578941A2 EP12187320.2A EP12187320A EP2578941A2 EP 2578941 A2 EP2578941 A2 EP 2578941A2 EP 12187320 A EP12187320 A EP 12187320A EP 2578941 A2 EP2578941 A2 EP 2578941A2
Authority
EP
European Patent Office
Prior art keywords
fuel
outlets
nozzle
hub
disposed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12187320.2A
Other languages
German (de)
English (en)
Other versions
EP2578941A3 (fr
Inventor
Abdul Rafey Khan
Bradley Donald Crawley
Donald Mark Bailey
Ajay Pratap Singh
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2578941A2 publication Critical patent/EP2578941A2/fr
Publication of EP2578941A3 publication Critical patent/EP2578941A3/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

Definitions

  • the subject matter disclosed herein relates to a fuel nozzle with an improved fuel injection design.
  • a gas turbine engine combusts a mixture of fuel and air to generate hot combustion gases, which in turn drive one or more turbines.
  • the hot combustion gases force turbine blades to rotate, thereby driving a shaft to rotate one or more loads, e.g., an electrical generator.
  • the gas turbine engine includes a fuel nozzle to inject fuel and air into a combustor.
  • the fuel air mixture significantly affects engine performance, fuel consumption, and emissions.
  • nonuniform mixing of fuel and air may increase emissions, e.g., nitrogen oxides (NO x ).
  • fuel may be injected via fuel outlets located on vanes disposed within the fuel nozzle.
  • limited space for fuel injection on the vanes may lead to poor flame holding margins and fuel distribution.
  • the invention resides in a system including a fuel nozzle.
  • the fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.
  • the invention resides in a system including a fuel nozzle.
  • the fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, and a swirl mechanism disposed in the airflow path.
  • the fuel nozzle also includes a first fuel path leading to multiple first fuel outlets directed into the airflow path upstream from the swirl mechanism.
  • the fuel nozzle further includes a second fuel path leading to multiple second fuel outlets directed into the airflow path, wherein the multiple second fuel outlets is downstream from the multiple first fuel outlets, and the first and second fuel paths are configured to supply independently controlled amounts of fuel to the multiple first and second outlets, respectively.
  • the invention resides in a system including a fuel nozzle.
  • the fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, a converging-diverging geometry disposed along the airflow path, multiple first fuel outlets directed into the airflow path along the converging diverging geometry, and multiple second fuel outlets directed into the airflow path at an axial offset distance from the converging-diverging geometry
  • the present disclosure is directed to systems for improving the injection of fuel (e.g., liquid and/or gas) into a fuel nozzle, thereby enhancing fuel wobbe capability (i.e., interchangeability of fuels used), flame holding margin (e.g., reducing the possibility of flame holding), premixing of the fuel (e.g., premixing fuel and air), and control over the fuel-air profile.
  • fuel e.g., liquid and/or gas
  • flame holding margin e.g., reducing the possibility of flame holding
  • premixing of the fuel e.g., premixing fuel and air
  • control over the fuel-air profile e.g., embodiments of the present disclosure include a distributed fuel injection circuit that enables injection of fuel (e.g., liquid and/or gas) via fuel outlets disposed on a hub or shroud upstream from fuel outlets located on vanes (e.g., swirl vanes) extending between the hub and the shroud.
  • vanes e.g., swirl vanes
  • the fuel nozzle includes a common fuel passage that splits fuel flow between the fuel outlets upstream of the vanes and the fuel outlets on the vanes enabling passive control of fuel between the respective fuel outlets.
  • the fuel nozzle includes separate fuel passages that enable independent fuel flows to fuel outlets upstream of the vanes and the fuel outlets on the vanes enabling active control (e.g., via a controller) of fuel to the respective fuel outlets.
  • the fuel outlets upstream of the vanes may be located on a converging-diverging geometry of the hub.
  • the fuel outlets upstream of the vanes may be oriented at an angle (e.g., less than 90 degrees relative to an axis of the fuel nozzle) in a downstream direction and/or circumferentially about the axis of the fuel nozzle to induce swirl about the axis.
  • the fuel outlets upstream of the vanes may be spaced circumferentially about the hub and/or include sets of fuel outlets axially offset from one another relative to the axis of the fuel nozzle.
  • each fuel nozzle 12 may include a distributed fuel injection circuit configured to enhance the fuel wobbe capability, flame holding margin, premixing of fuel with air, and control over the fuel-air profile in the fuel nozzle 12.
  • the turbine system 10 may use liquid and/or gas fuel, such as natural gas and/or a hydrogen rich synthetic gas, to drive the turbine system 10.
  • one or more fuel nozzles 12 intake a fuel supply 14 (e.g., liquid and/or gas fuel), mix the fuel with air, and distribute the air-fuel mixture into a combustor 16 in a suitable ratio for optimal combustion, emissions, fuel consumption, and power output.
  • the distributed fuel injection circuit may provide fuel to fuel outlets disposed in a region of a swirl mechanism 11 (e.g., on swirl vanes) and fuel outlets upstream from the swirl mechanism 11.
  • the fuel outlets upstream from the swirl mechanism 11 may be disposed on a hub 13 (e.g., on a converging-diverging geometry 15) and/or a shroud 17 of the fuel nozzle 12.
  • the turbine system 10 may include one or more fuel nozzles 12 located inside one or more combustors 16. The air-fuel mixture combusts in a chamber within the combustor 16, thereby creating hot pressurized exhaust gases.
  • the combustor 16 directs the exhaust gases through a turbine 18 toward an exhaust outlet 20. As the exhaust gases pass through the turbine 18, the gases force turbine blades to rotate a shaft 22 along an axis of the turbine system 10. As illustrated, the shaft 22 may be connected to various components of the turbine system 10, including a compressor 24.
  • the compressor 24 also includes blades coupled to the shaft 22. As the shaft 22 rotates, the blades within the compressor 24 also rotate, thereby compressing air from an air intake 26 through the compressor 24 and into the fuel nozzles 12 and/or combustor 16.
  • the shaft 22 may also be connected to a load 28, which may be a vehicle or a stationary load, such as an electrical generator in a power plant or a propeller on an aircraft, for example.
  • the load 28 may include any suitable device capable of being powered by the rotational output of the turbine system 10.
  • FIG. 2 is a cross-sectional side view of an embodiment of the fuel nozzle 12, as illustrated in FIG. 1 , with the fuel nozzle 12 having an improved fuel injection design to enhance the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions.
  • the fuel nozzle 12 e.g., turbine fuel nozzle
  • the fuel nozzle 12 is configured to mount in the combustor 16 (e.g., turbine combustor) of the gas turbine engine 10.
  • the fuel nozzle 12 includes a center body 38 (e.g., annular inner body), the swirl mechanism 11, and the shroud 17 (e.g., annular outer body), each disposed about an axis 42.
  • the center body 38 includes the hub 13 (e.g., an annular wall) disposed inside and concentric with the shroud 17, wherein the shroud 17 and the hub 13 are offset from one another by a radial gap 46.
  • the swirl mechanism 11 includes a plurality of vanes 48 (e.g., swirl vanes).
  • the vanes 48 extend radially in directions 50 and 52 between the shroud 17 and the hub 13, and are distributed circumferentially 54 about the axis 42.
  • the shroud 17 is circumferentially 54 disposed about the hub 13 and the plurality of vanes 48, with the vanes 48 extending between the hub 13 and shroud 17.
  • the fuel nozzle 12 may include any number of vanes 48.
  • the fuel nozzle 12 may include 1 to 20 or 2 to 10 vanes 48, or any number therebetween.
  • the center body 38 also includes fuel passage 56.
  • a controller 58 controls the flow of fuel via a valve 60 from a fuel supply 62 to the fuel nozzle 12 (e.g., fuel passage 56).
  • the fuel passage 56 includes a common fuel passage 64 that extends through the inner body 38 and leads to a plurality of first fuel outlets 66 disposed on the hub 13 and a plurality of second fuel outlets 68 disposed in the region of the swirl mechanism 11 (e.g., on the plurality of vanes 48). As illustrated, the plurality of first fuel outlets 66 is disposed upstream from the plurality of second fuel outlets 68.
  • the common fuel passage 64 splits a fuel flow between the first fuel outlets 66 and the second fuel outlets 68 as indicated by arrows 70 and 72. Approximately 30 percent or less of the total fuel in the common fuel passage 64 may be diverted to the first fuel outlets 66.
  • the common fuel passage 64 enables passive control over the injection of fuel via the fuel outlets 66 and 68.
  • the first fuel outlets 66 are disposed on the hub 13 upstream from the swirl mechanism 11 (e.g., vanes 48). In particular, the first fuel outlets 66 are disposed on the converging-diverging geometry 15 of the hub 13 along an airflow path 74.
  • the converging-diverging geometry 15 includes a converging portion 76 that gradually converges toward the shroud 17 in an axial direction 77 and a diverging portion 78 that gradually diverges away from the shroud 17 in the axial direction 77.
  • the diverging portion 78 is disposed downstream of the converging portion 76 in the axial direction 77.
  • the first fuel outlets 66 may be disposed on another portion of the hub 13 (e.g., besides the converging-diverging geometry 15) upstream of the swirl mechanism 11.
  • the plurality of second fuel outlets 68 is disposed at an axially offset distance 79 downstream from the converging diverging geometry 15.
  • the first fuel outlets 66 are oriented outward in the radial directions 50 and 52 (i.e. crosswise) relative to the axis 42 of the fuel nozzle 12. In some embodiments, the first fuel outlets 66 may also be distributed on the shroud 17 (see FIG. 3 ) upstream of the swirl mechanism 11.
  • the illustrated fuel outlets 66 may each represent one or more fuel outlets 66 disposed circumferentially 54 about the hub 13 (see FIGS. 6 and 7 ).
  • each vane 48 includes one or more fuel outlets 68.
  • each vane 48 may include a first set 80 of fuel outlets 68 and a second set 82 of fuel outlets 68 axially offset from each other along the axis 42 of the fuel nozzle 12 in the axial (i.e., downstream) direction 77.
  • the number of fuel outlets 68 on each vane 48 may range from 1 to 50, 1 to 10, 4 to 20, or 4 to 10, or any other number.
  • each vane 48 may include one or more fuel outlets 68 (e.g., 1 to 10) on each side.
  • the plurality of vanes 48 is configured to swirl or rotate the air flow, while mixing fuel with air.
  • the common fuel passage 64 splits the fuel flow into a first fuel flow 70 to the plurality of first fuel outlets 66 and a second fuel flow 72 to the plurality of second fuel outlets 68.
  • fuel e.g., gas fuel
  • the fuel exits the fuel outlets 66 disposed on the hub 13 crosswise to the axis 42 of the fuel nozzle 12.
  • the fuel nozzle 12 include the airflow path (e.g., annular flow path), generally indicated by arrow 74, between the hub 13 and the shroud 17. Air flows in the axial direction 77 into the first mixing region 86. In the first mixing region 86, the fuel from the fuel outlets 66 interacts with the air. The fuel-air mixture 88 flows downstream towards the swirl mechanism 11 (e.g., blades 48) disposed in the airflow path 74. Another portion of the fuel exits the second fuel outlets 68 into a second mixing region 90. The fuel-air mixture 88 flows through the airflow path 74 into the second mixing region 90 surrounding each vane 48.
  • the airflow path e.g., annular flow path
  • each vane 48 fuel from the fuel outlets 68 interacts with the fuel-air mixture 88 to form a fuel-air mixture 92.
  • the fuel-air mixture 92 is swirled by the vanes 48 to aid in mixing of the fuel and air for proper combustion, and flows downstream towards an exit 94 of the fuel nozzle 12, as generally indicated by arrows 96.
  • the injection of fuel upstream of the swirl mechanism 11 enhances the flame holding margins (e.g., reducing the possibility of flame holding) around the vanes 48.
  • diverting a portion of the fuel for upstream injection enables a reduction in a diameter 98 of the fuel outlets 68 on the vanes 48 enhancing the flame holding margin.
  • the reduction in diameter 98 of the fuel outlet 68 relative to a typical fuel outlet 68 may range from approximately 1 to 99 percent, 10 to 90 percent, 20 to 80 percent, 30 to 70 percent, or 40 to 60 percent, and all subranges therebetween.
  • the reduction in diameter 98 of the fuel outlet 68 may be approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, or 95 percent, or any other number.
  • the improved fuel injection design enhances premixing efficiencies which reduces emissions.
  • the improved fuel injection design provides fuel injection from both a circumferential direction 54 and radial direction 50 and 52 to provide better control over the overall fuel-air profile of the fuel nozzle 12 and, thus, improve the dynamics and operability of the fuel nozzle 12. Further, the improved fuel injection design enhances wobbe capability and fuel flexibility for the fuel nozzle 12.
  • FIG. 3 is a cross-sectional side view of an embodiment of the fuel nozzle 12, as illustrated in FIG. 1 , with the fuel nozzle 12 having an improved fuel injection design to enhance the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions.
  • the fuel nozzle 12 of FIG. 3 is as described in FIG.
  • the fuel nozzle 12 includes fuel outlets 66 disposed on the shroud 17 upstream of the swirl mechanism 11 and separate fuel passages for the fuel outlets 66 and 68.
  • the center body 38 of the fuel nozzle 12 includes fuel passage 56, fuel passages 110, and fuel passages 112.
  • the fuel passage 56 provides a fuel flow (e.g., fuel path 111) to the fuel outlets 68 disposed on the vanes 48.
  • the fuel passages 110 and 112 provide fuel flows (e.g., fuel paths 113) to the fuel outlets 66 disposed on the hub 13 and shroud 17, respectively.
  • the fuel paths 111 and 113 are configured to supply independently controlled amounts of fuel to the fuel outlets 68 and 66, respectively.
  • a controller 58 controls the flow of fuel via valves 60, 114, and 116 from respective fuel supplies 62, 118, and 120 to the respective fuel passages 56, 110, and 112.
  • the fuel e.g., gas and/or liquid fuel
  • the controller 58 includes a fuel split control 122 configured to control the fuel flows to the outlets 66 and 68 independent from one another.
  • the different fuel passages 56, 110, and 112 in conjunction with the controller 58 enables active control of fuel injection via the fuel outlets 66 and 68 and, thus, the ability to change fuel pressure and fuel pressure dynamics.
  • the fuel split control 122 may actively adjust the split of the fuel (e.g., ratio of fuel flows into the fuel passages 56, 110, and 112 or percent of fuel to each set of fuel outlets 66 and 68).
  • the plurality of first fuel outlets 66 are disposed on the hub 13 (e.g., along the converging-diverging geometry 15). Each illustrated fuel outlet 66 may represent one or more fuel outlets 66 circumferentially 54 disposed about the axis 42 of the fuel nozzle 12 (see FIGS. 6 and 7 ).
  • the plurality of first fuel outlets 66 includes a first set 124 of first fuel outlets 66, a second set 126 of first fuel outlets 66, and a third set 128 of first fuel outlets 66.
  • the first, second, and third sets 124, 126, and 128 of fuel outlets 66 are axially offset from one another relative to the axis 42 of the first fuel nozzle 12.
  • each fuel outlet 66 is directed into the airflow path 74.
  • each fuel outlet 66 is oriented at an angle 130 relative to the axis 42 of the fuel nozzle 12.
  • the fuel outlets 66 may be oriented at the angle 130 in an upstream (e.g., axial) direction 132 (e.g., third set 128 of the fuel outlets 66) or the downstream (e.g., axial) direction 77 (e.g., first set 124 of the fuel outlets 66) along the airflow path 74.
  • the fuel outlets 66 may be oriented directly perpendicular (e.g., crosswise) to the airflow path 74 (e.g., second set 126 of the fuel outlets 66).
  • each fuel outlet 66 may range from approximately 0 to 180 degrees, 0 to 90 degrees, 90 to 180 degrees, 0 to 45 degrees, 45 to 90 degrees, 90 to 135 degrees, or 135 to 180 degrees, and all subranges therebetween.
  • the angle 130 may be approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140, 150, 160, 170, or 180 degrees, or any other angle.
  • each fuel outlet 66 is oriented at the angle 130 in the downstream direction 77 along the airflow path 74, where the angle 130 is less than approximately 90 degrees relative to the axis 42 of the fuel nozzle 12 (see FIG. 5 ).
  • each fuel outlet 66 of the plurality of first outlets 66 is oriented at an angle circumferentially about the axis 42 of the fuel nozzle 12 to induce an injected fuel to swirl about the axis 42, where the angle is less than 90 degrees relative to the axis 42 (see FIG. 7 ).
  • the fuel nozzle 12 also includes the plurality of first outlets 66 disposed on the shroud 17.
  • the first outlets 66 are located along a converging-diverging geometry 134.
  • the converging-diverging geometry 134 is similar to the converging-diverging geometry 15.
  • the first outlets 66 may be disposed upstream of the swirl mechanism 11 (e.g., vanes 48) on a portion of the shroud 17 different from the converging-diverging geometry 134.
  • the first outlets 66 disposed on the shroud 17 are similar to the first outlets 66 disposed on the hub 13.
  • the plurality of first outlets 66 on the shroud 17 may be disposed directly across from the plurality of first outlets 66 on the hub 13 (and converging-diverging geometry 15).
  • the plurality of first outlets 66 on the shroud 17 may be axially offset from the plurality of fuel outlets 66 on the hub 13 along the axis 42 of the fuel nozzle 12.
  • fuel flows into fuel passages 110 and 112 as indicated by arrows 136 and 138, respectively.
  • fuel e.g., liquid and/or gas fuel
  • fuel e.g., liquid and/or gas fuel
  • the fuel exits the fuel outlets 66 disposed on the hub 13 and shroud 17 crosswise to the axis 42 of the fuel nozzle 12.
  • the fuel outlets 66 disposed on the hub 13 and shroud 17 are oriented crosswise to one another (e.g., in outward 50 and inward 52 radial directions, respectively) and to axis 42.
  • the fuel nozzle 12 include the airflow path (e.g., annular flow path), generally indicated by arrow 74, between the hub 13 and the shroud 17. Air flows in the axial direction 54 into the first mixing region 86. In the first mixing region 86 the fuel from the fuel outlets 66 interacts with the air.
  • the fuel-air mixture 88 flows downstream towards the swirl mechanism 11 (e.g., blades 48) disposed in the airflow path 74.
  • the plurality of second fuel outlets 68 is disposed in a region of the swirl mechanism 11 (e.g., on the swirl vanes 48). Fuel flows into the fuel path 111 leading to the plurality of second fuel outlets 68 directed into the airflow path 74. In particular, fuel flows into fuel passage 56 as indicated by arrows 140, and flows to the fuel outlets 68 on the vanes 48 as indicated by arrows 72. Fuel exits the second fuel outlets 68 into the second mixing region 90.
  • the fuel-air mixture 88 flows through the airflow path 74 into the second mixing region 90 surrounding each vane 48. In the mixing region 90 of each vane 48, fuel from the fuel outlets 68 interacts with the fuel-air mixture 88 to form a fuel-air mixture 90.
  • the fuel-air mixture 90 is swirled by the vanes 48 to aid in mixing of the fuel and air for proper combustion, and flows downstream towards the exit 94 of the fuel nozzle 12, as generally indicated by arrows 96.
  • the injection of fuel upstream of the swirl mechanism 11 enhances the flame holding margins around the vanes 48.
  • diverting a portion of the fuel for upstream injections enables a reduction in a diameter 98 of the fuel outlets 68 on the vanes 48 enhancing the flame holding margin.
  • the reduction in diameter 98 of the fuel outlet 68 relative to a typical fuel outlet 68 may range from approximately 1 to 99 percent, 10 to 90 percent, 20 to 80 percent, 30 to 70 percent, or 40 to 60 percent, and all subranges therebetween.
  • the reduction in diameter 98 of the fuel outlet 68 may be approximately 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, or 95 percent, or any other number.
  • the improved fuel injection design improves premixing efficiencies which reduces emissions.
  • the improved fuel injection design provides fuel injection from both a circumferential direction 54 and radial direction 50 and 52 to provide better control over the overall fuel-air profile of the fuel nozzle 12 and, thus, improves the dynamics and operability of the fuel nozzle 12.
  • the improved fuel injection design enables a staged mixing of fuel with air.
  • the improved fuel injection design enhances wobbe capability and fuel flexibility for the fuel nozzle 12.
  • the multiple fuel passages 56, 111, and 113 enable different fuels (e.g., liquid and/or gas fuels) to be employed with the fuel nozzle 12.
  • FIGS. 4-7 illustrate various embodiments of the arrangement of the fuel outlets 66 upstream of the swirl mechanism 11.
  • the arrangement of the fuel outlets 66 upstream of the swirl mechanism 11 enhances the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions (e.g., NOx) in the turbine system 10.
  • FIG. 4 is a partial cross-sectional side view of an embodiment of the fuel nozzle 12 of FIG. 2 , taken within line 4-4, illustrating multiple fuel outlets 66.
  • the converging-diverging geometry 15 of the hub 13 includes the plurality of first fuel outlets 66.
  • the converging-diverging geometry 15 is as described in FIG. 2 .
  • Each illustrated fuel outlet 66 may represent one or more fuel outlets 66 circumferentially 54 disposed about the axis 42 of the fuel nozzle 12 (see FIGS. 6 and 7 ).
  • the plurality of first fuel outlets 66 includes the first set 124 of first fuel outlets 66, the second set 126 of first fuel outlets 66, and the third set 128 of first fuel outlets 66.
  • the first, second, and third sets 124, 126, and 128 of fuel outlets 66 are axially offset from one another relative to the axis 42 of the first fuel nozzle 12.
  • each fuel outlet 66 is directed into the airflow path 74.
  • each fuel outlet 66 is oriented at the angle 130 relative to the axis 42 of the fuel nozzle 12.
  • the illustrated fuel outlets 66 are oriented directly perpendicular (e.g., crosswise) in radial direction 50 to the airflow path 74 with each fuel outlet 66 including the angle 130 of 90 degrees relative to the axis 42 of the fuel nozzle 12.
  • the fuel outlets 66 may be oriented at the angle 130 in an upstream (e.g., axial) direction 132 (e.g., third set 128 of the fuel outlets 66) or the downstream (e.g., axial) direction 77 (e.g., first set 124 of the fuel outlets 66) along the airflow path 74 (see FIG. 3 ).
  • the angle 130 of each fuel outlet 66 relative to the axis 42 of the fuel nozzle 12 may range from approximately 0 to 180 degrees, 0 to 90 degrees, 90 to 180 degrees, 0 to 45 degrees, 45 to 90 degrees, 90 to 135 degrees, or 135 to 180 degrees, and all subranges therebetween.
  • the angle 130 may be approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140, 150, 160, 170, or 180 degrees, or any other angle.
  • each fuel outlet 66 may include a diameter 150.
  • the diameter 150 of each fuel outlet 66 may range from approximately 0.5 to 1.8 mm, 0.75 to 1.55 mm, 1 to 1.3 mm, 0.5 to 1.0 mm, 1 to 1.8 mm, 1.3 to 1.8 mm, and all subranges therebetween.
  • the diameter 150 each fuel outlet 66 may be approximately 0.5, 0.6., 0.7, 0.8, 0.9, 1.0, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, or 1.8 mm, or any other number therebetween.
  • the diameter 150 of each fuel outlet 66 may be the same or different at different axial positions. The difference in diameter 150 between fuel outlets 66 may vary by approximately 10 to 200 percent relative to one another.
  • the diameter 150 of the fuel outlets 66 may vary by approximately 10 to 100 percent, 10 to 50 percent, 50 to 100 percent, 100 to 200 percent, 100 to 150 percent, 150 to 200 percent, and all subranges therebetween.
  • the diameter 150 between fuel outlets 66 may vary by approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140, 150, 160, 170, 180, 190, or 200 percent, or any other number therebetween.
  • FIG. 5 is a partial cross-sectional side view of an embodiment of the fuel nozzle 12 of FIG. 2 taken within line 4-4 that illustrates an angled fuel outlet 66.
  • the converging-diverging geometry 15 of the hub 13 includes the plurality of first fuel outlets 66.
  • the converging-diverging geometry 15 is as described in FIG. 2 .
  • Each illustrated fuel outlet 66 may represent one or more fuel outlets 66 circumferentially 54 disposed about the axis 42 of the fuel nozzle 12 (see FIGS. 6 and 7 ). As illustrated, the fuel outlets 66 are directed into the airflow path 74.
  • each fuel outlet 66 is oriented at the angle 130 in the downstream direction 77 along the airflow path 74, where the angle 130 is less than approximately 90 degrees relative to the axis 42 of the fuel nozzle 12. Angling the fuel injection downstream enables premixing of the fuel and air without impeding the flow through the airflow path 74.
  • FIG. 6 is a cross-sectional view of an embodiment of the fuel nozzle 12 of FIG. 2 taken along line 6-6 that illustrates multiple fuel outlets 66.
  • the fuel nozzle 12 includes the hub 13, the shroud 17, and the plurality of the first fuel outlets 66 disposed about the axis 42.
  • the fuel outlets 66 are circumferentially 54 disposed about the axis 42 of the fuel nozzle 12.
  • fuel outlet 66 disposed on the hub 13 is directed into the airflow path 74 and oriented crosswise to the axis 42.
  • Each fuel outlet 66 is oriented at an angle 160 circumferentially about the axis 42 (e.g., relative to a tangent line (illustrated dashed line)).
  • each fuel outlet 66 circumferentially about the axis 42 of the fuel nozzle 12 may range from approximately 0 to 180 degrees, 0 to 90 degrees, 90 to 180 degrees, 0 to 45 degrees, 45 to 90 degrees, 90 to 135 degrees, or 135 to 180 degrees, and all subranges therebetween.
  • the angle 160 may be approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140, 150, 160, 170, or 180 degrees, or any other angle.
  • each fuel outlet 66 includes the angle 160 of approximately 90 degrees.
  • Each fuel outlet 66 is configured to inject fuel radially 50 and 52 into the airflow path 74 as indicated by arrows 162 to mix fuel with air flowing in axial direction 77.
  • each fuel outlet 66 is oriented at the angle 160 circumferentially about the axis 42 of the fuel nozzle 12 (e.g., relative to a tangent line (illustrated dashed line)). As illustrated, the angle 160 is less than approximately 90 degrees relative to the axis 42. The angle 160 may range from approximately 20 to 70 degrees, 30 to 60 degrees, 40 to 50 degrees, and all subranges therebetween.
  • the angle 160 may be approximately 10, 15, 20, 25, 30, 40, 45, 50, 55, 60, 65, 70, 75, 80, or 85 degrees, or any other angle.
  • the angled fuel outlets 66 are configured to induce injected fuel to swirl circumferentially 54 about the axis as indicated by arrows 172.
  • the induction of swirl may increase the premixing efficiency between the fuel and air.
  • FIG. 8 is a partial cross-sectional view of an embodiment of the fuel nozzle 12 of FIG. 2 taken within line 4-4 that illustrates a converging-straight-diverging geometry 182 with the fuel outlet 66.
  • the converging-straight-diverging geometry 182 includes the converging portion 76 that gradually converges toward the hub 13 in the axial direction 77, a straight portion 184 that remains constant relative to the hub 13, and the diverging portion 78 that gradually diverges away from the hub 13 in the axial direction 77.
  • the diverging portion 78 is disposed downstream of the converging portion 76 and the straight portion 184 in the axial direction 77.
  • the straight portion 184 is disposed downstream of the converging portion 76 in the axial direction 77.
  • the fuel outlet 66 may represent one or more fuel outlets 66 disposed circumferentially about the hub 13.
  • the geometry 184 may include multiple sets of fuel outlets 66 axially offset from one another relative to the axis 42 of the fuel nozzle 12.
  • the fuel outlets 66 may be disposed on the converging portion 76, straight portion 184, and/or diverging portion 78. In certain embodiments, the fuel outlets 66 may be angled as described above.
  • the geometries 15 and 184 of the hub 13 with the fuel outlets 66 are only examples of various geometries. In certain embodiments, the arrangement and shape of the geometry of the hub 13 with the fuel outlets 66 may vary from the geometries 15 and 184.
  • Fuel outlets 66 located upstream from fuel injection in the region of the swirl mechanism 11 enable hub 13 and shroud 17 injection of fuel crosswise to the airflow.
  • the fuel may be distributed between these fuel outlets 66 for cross-flow injection at a variety of angles (e.g., 0 to 90 degrees).
  • the improved design enhances the fuel wobbe capability, flame holding margin, premixing of the fuel, and control over the fuel-air profile, while reducing emissions (e.g., NOx) in the turbine system 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Fuel-Injection Apparatus (AREA)
EP12187320.2A 2011-10-07 2012-10-04 Système d'injection de carburant dans un injecteur de carburant Withdrawn EP2578941A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/269,510 US8850821B2 (en) 2011-10-07 2011-10-07 System for fuel injection in a fuel nozzle

Publications (2)

Publication Number Publication Date
EP2578941A2 true EP2578941A2 (fr) 2013-04-10
EP2578941A3 EP2578941A3 (fr) 2014-04-02

Family

ID=46968083

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12187320.2A Withdrawn EP2578941A3 (fr) 2011-10-07 2012-10-04 Système d'injection de carburant dans un injecteur de carburant

Country Status (3)

Country Link
US (1) US8850821B2 (fr)
EP (1) EP2578941A3 (fr)
CN (1) CN103032899A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104633710A (zh) * 2015-02-10 2015-05-20 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室双燃料喷嘴
CN104896512A (zh) * 2015-05-11 2015-09-09 北京航空航天大学 一种宽稳定工作范围的低排放天然气燃烧室
WO2015165680A1 (fr) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Brûleur à profil de combustible radial réglable

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US9650959B2 (en) * 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9366439B2 (en) 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
US9347668B2 (en) 2013-03-12 2016-05-24 General Electric Company End cover configuration and assembly
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US10731861B2 (en) * 2013-11-18 2020-08-04 Raytheon Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine
EP2933560B1 (fr) * 2014-04-17 2017-12-06 Ansaldo Energia Switzerland AG Procédé de prémélange d'air avec un combustible gazeux et ensemble brûleur pour la mise en oeuvre dudit procédé
EP3207312B1 (fr) * 2014-10-17 2020-08-26 Nuovo Pignone S.r.l. Procédé pour la réduction des émissions de nox dans une turbine à gaz, mélangeur air-carburant, turbine à gaz et dispositif de tourbillonnement
US10578306B2 (en) * 2017-06-16 2020-03-03 General Electric Company Liquid fuel cartridge unit for gas turbine combustor and method of assembly
US11408356B2 (en) 2017-10-03 2022-08-09 General Electric Company Method of operating a combustion system with main and pilot fuel circuits
KR102096580B1 (ko) * 2019-04-01 2020-04-03 두산중공업 주식회사 예혼합 균일성이 향상된 연소기 노즐 및 이를 구비하는 가스터빈용 연소기
KR102164619B1 (ko) * 2019-04-08 2020-10-12 두산중공업 주식회사 연소기 및 이를 포함하는 가스터빈
JP7257358B2 (ja) * 2020-05-01 2023-04-13 三菱重工業株式会社 ガスタービン燃焼器
WO2022079523A1 (fr) * 2020-10-14 2022-04-21 King Abdullah University Of Science And Technology Injecteur réglable de carburant pour commande de dynamique de flamme
KR102382634B1 (ko) * 2020-12-22 2022-04-01 두산중공업 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
KR102459999B1 (ko) * 2021-01-13 2022-10-26 두산에너빌리티 주식회사 연소기용 노즐, 연소기, 및 이를 포함하는 가스 터빈
CN113339844B (zh) * 2021-06-22 2022-11-18 西安航天动力研究所 一种空气氢气喷注单元及其燃烧组织方法
US11815269B2 (en) 2021-12-29 2023-11-14 General Electric Company Fuel-air mixing assembly in a turbine engine
US12072103B2 (en) 2021-12-30 2024-08-27 General Electric Company Turbine engine fuel premixer
US20240263791A1 (en) * 2023-02-02 2024-08-08 Pratt & Whitney Canada Corp. Hydrogen fuel distributor
US20240263786A1 (en) * 2023-02-02 2024-08-08 Pratt & Whitney Canada Corp. Central air passage with radial fuel distributor
US11946644B1 (en) * 2023-03-31 2024-04-02 Solar Turbines Incorporated Multi-pot swirl injector

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5284438A (en) * 1992-01-07 1994-02-08 Koch Engineering Company, Inc. Multiple purpose burner process and apparatus
DE69515931T2 (de) 1994-06-10 2000-11-02 General Electric Co., Schenectady Regelung einer Gasturbinenbrennkammer
DE19532264C2 (de) 1995-09-01 2001-09-06 Mtu Aero Engines Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
JP4508474B2 (ja) * 2001-06-07 2010-07-21 三菱重工業株式会社 燃焼器
US6655145B2 (en) * 2001-12-20 2003-12-02 Solar Turbings Inc Fuel nozzle for a gas turbine engine
US6691515B2 (en) 2002-03-12 2004-02-17 Rolls-Royce Corporation Dry low combustion system with means for eliminating combustion noise
GB2404729B (en) * 2003-08-08 2008-01-23 Rolls Royce Plc Fuel injection
US6993916B2 (en) 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
US7836698B2 (en) 2005-10-20 2010-11-23 General Electric Company Combustor with staged fuel premixer
US7640725B2 (en) * 2006-01-12 2010-01-05 Siemens Energy, Inc. Pilot fuel flow tuning for gas turbine combustors
US7908864B2 (en) 2006-10-06 2011-03-22 General Electric Company Combustor nozzle for a fuel-flexible combustion system
US7966820B2 (en) 2007-08-15 2011-06-28 General Electric Company Method and apparatus for combusting fuel within a gas turbine engine
US9140454B2 (en) 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
US20100192582A1 (en) * 2009-02-04 2010-08-05 Robert Bland Combustor nozzle
US8607569B2 (en) 2009-07-01 2013-12-17 General Electric Company Methods and systems to thermally protect fuel nozzles in combustion systems

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015165680A1 (fr) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Brûleur à profil de combustible radial réglable
CN104633710A (zh) * 2015-02-10 2015-05-20 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室双燃料喷嘴
CN104896512A (zh) * 2015-05-11 2015-09-09 北京航空航天大学 一种宽稳定工作范围的低排放天然气燃烧室

Also Published As

Publication number Publication date
CN103032899A (zh) 2013-04-10
US8850821B2 (en) 2014-10-07
US20130086910A1 (en) 2013-04-11
EP2578941A3 (fr) 2014-04-02

Similar Documents

Publication Publication Date Title
US8850821B2 (en) System for fuel injection in a fuel nozzle
US8850822B2 (en) System for pre-mixing in a fuel nozzle
US8925323B2 (en) Fuel/air premixing system for turbine engine
EP2541143B1 (fr) Prémélangeur injecteur de carburant pour moteur à turbine à gaz
US9115896B2 (en) Fuel-air mixer for use with a combustor assembly
US20120180487A1 (en) System for flow control in multi-tube fuel nozzle
US10415479B2 (en) Fuel/air mixing system for fuel nozzle
US20130025285A1 (en) System for conditioning air flow into a multi-nozzle assembly
US20100300102A1 (en) Method and apparatus for air and fuel injection in a turbine
US10215414B2 (en) System and method having fuel nozzle
CN109804200B (zh) 旋流器、燃烧装置组件以及具有改善燃料/空气混合的燃气涡轮
US20100275601A1 (en) Turbine air flow conditioner
US20110107765A1 (en) Counter rotated gas turbine fuel nozzles
US20120111013A1 (en) System for directing air flow in a fuel nozzle assembly
US10458655B2 (en) Fuel nozzle assembly
US10823420B2 (en) Pilot nozzle with inline premixing
US9322336B2 (en) Fuel nozzle for gas turbine
US20170122211A1 (en) Turbine engine fuel injection system and methods of assembling the same
CA3010044C (fr) Chambre de combustion pour turbine a gaz
US20150276225A1 (en) Combustor wth pre-mixing fuel nozzle assembly
US9441835B2 (en) System and method for fuel and steam injection within a combustor
JP4477039B2 (ja) ガスタービンエンジンの燃焼装置
US12072103B2 (en) Turbine engine fuel premixer

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/36 20060101ALI20140227BHEP

Ipc: F23R 3/28 20060101ALI20140227BHEP

Ipc: F23R 3/20 20060101ALI20140227BHEP

Ipc: F23R 3/14 20060101AFI20140227BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20141003